CN114837811A - Combined power mode conversion method for extended outer casing - Google Patents
Combined power mode conversion method for extended outer casing Download PDFInfo
- Publication number
- CN114837811A CN114837811A CN202210411274.4A CN202210411274A CN114837811A CN 114837811 A CN114837811 A CN 114837811A CN 202210411274 A CN202210411274 A CN 202210411274A CN 114837811 A CN114837811 A CN 114837811A
- Authority
- CN
- China
- Prior art keywords
- channel
- turbine
- turbine engine
- flow
- inlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000006243 chemical reaction Methods 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 41
- 230000007246 mechanism Effects 0.000 claims abstract description 11
- 230000008602 contraction Effects 0.000 claims abstract description 5
- 230000008569 process Effects 0.000 abstract description 25
- 230000008859 change Effects 0.000 abstract description 6
- 230000003247 decreasing effect Effects 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a combined power mode conversion method for an extended outer casing, which aims at an axisymmetric air inlet channel, wherein the axisymmetric air inlet channel comprises the following steps: a centerbody, an inlet lip shroud surrounding the centerbody, an inlet shroud, an extendable turbine engine case; the size of the inlet of the turbine channel is adjusted by controlling the extension and the contraction of the turbine engine outer casing, so that the turbine channel is controlled to be opened or closed, the switching of the gas path and the redistribution of the flow are completed, and the mode conversion is realized. The invention has simple mechanism and strong feasibility, does not increase complex mechanical structure, changes the flow area of the inlet of the turbine channel through the telescopic length of the outer casing, and realizes the change of the flow path of air flow before and after the mode conversion process.
Description
Technical Field
The invention relates to the field of mode conversion of air inlet channels, in particular to a combined power mode conversion method of an extended outer casing.
Background
The air inlet channel is a key part of an air-breathing combined power engine, and has the main function of providing gas with certain pressure, temperature, speed and flow rate to a compressor of a turbine engine or a combustion chamber of a ramjet engine, wherein in a mode conversion process (the working state of the turbine engine is converted to the working state of the ramjet engine or the working state of the ramjet engine is converted to the working state of the turbine engine), the air inlet channel needs to provide air flow to the two engines simultaneously. According to the structural form of the TBCC air inlet, the air inlet can be divided into a binary air inlet, an axisymmetric air inlet and other forms of air inlets. The axisymmetric air inlet has the characteristics of simple structure, high utilization rate of the windward side, high compression efficiency, good reasoning performance and the like, and is widely applied.
The mode conversion process refers to the process of converting the turbine working mode to the high-Mach-number stamping mode or converting the stamping working mode to the turbine working mode when the Mach number is low, and the key of whether the thrust and the flow can be stably transited is the success or failure of the mode conversion process. Therefore, the modal transformation technique is a key technique in the research content of TBCC engines. In the mode conversion technology, how to realize switching of the flow paths under the condition of low loss is one of the technical difficulties, so the air inlet channel mode conversion technology is the key point in the research of the mode conversion technology.
Disclosure of Invention
In view of this, the present invention provides a method for converting a combined power mode of an extended outer casing, so as to solve the problem of mode conversion of a tandem type combined power engine using an axisymmetric intake duct; the size of the inlet of the turbine channel is changed and the opening and closing process is realized by extending the outer casing of the turbine engine and adjusting the extension length of the outer casing, the flow path change of air flow before and after the mode conversion process is realized, and the requirement of the turbine engine or the ramjet on the flow is met when the turbine engine or the ramjet works independently; in the mode conversion process, the flow distribution of the turbine and the ram channel in the mode conversion process is adjusted, and meanwhile, the flow requirements of the turbine engine and the ram engine in the mode conversion process are met.
In order to achieve the purpose, the invention adopts the following technical scheme:
a combined power mode conversion method for an extended outer case, said conversion method being directed to an axisymmetric inlet duct for a tandem combined power engine including a ram channel and a turbine channel outer ring, the axisymmetric inlet duct comprising: a centerbody, an inlet lip shroud surrounding the centerbody, an inlet shroud, an extendable turbine engine case;
the center body is supported by the center body on a turbine engine center fairing;
the air inlet lip cover is arranged on the outer edge of the air inlet cover, wherein a throat is formed between the middle part of the central body and the air inlet lip cover;
the turbine engine outer casing is arranged inside the air inlet channel, and the inside of the air inlet channel is divided into a stamping channel and a turbine channel;
the size of the inlet of the turbine channel is adjusted by controlling the extension and the contraction of the turbine engine outer casing, so that the turbine channel is controlled to be opened or closed, the switching of the gas path and the redistribution of the flow are completed, and the mode conversion is realized.
Furthermore, the extension and contraction of the turbine engine outer case is realized by arranging a telescopic mechanism at the front end of the turbine engine outer case and adjusting the length of the telescopic mechanism.
Further, the shortest distance of the forward extension of the telescopic mechanism is determined by the flow demanded by the turbine engine in the turbine mode, and the longest distance is determined by the extension distance required by the turbine passage to be completely closed.
Further, the diameter of the middle part of the central body is larger than or equal to the diameter of the turbine engine outer casing.
The invention has the beneficial effects that:
the mechanism is simple, the feasibility is strong, a complex mechanical structure is not increased, the flow area of the inlet of the turbine channel is changed through the telescopic length of the outer casing, the change of the flow path of air flow before and after the mode conversion process is realized, part of the air flow provided by the air inlet channel flows into the turbine engine when the turbine engine works alone to meet the flow demand of the turbine engine, and the air flow does not flow into the turbine engine any more but flows into the channel of the ramjet engine when the ramjet engine works alone to meet the increase of the flow demand of the ramjet engine when the ramjet engine works at a high Mach number; in the mode conversion process, the flow redistribution of the turbine and the stamping channel is realized by the adjusting scheme, the change of the flow demand of the turbine engine and the stamping engine in the mode conversion process can be simultaneously met, and the stable transition of the thrust and the flow in the mode conversion process of the air-breathing combined power engine is realized.
Drawings
FIG. 1 is a schematic structural diagram of an axisymmetrical inlet duct provided in embodiment 1 in a state where a turbine passage is fully opened;
FIG. 2 is a schematic diagram of an implementation of the combined power mode conversion method provided in embodiment 1;
FIG. 3 is a schematic illustration of the flow change during the turbine to ram mode transition;
in the drawings:
1-movable central body, 2-inlet lip cover, 3-inlet cover, 4-turbine engine outer casing, 5-punching channel, 6-turbine channel and 7-central body support.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
Referring to fig. 1 to 3, the present embodiment provides a combined power mode conversion method for an extended outer casing, and specifically, as shown in fig. 1, the fig. 1 shows an axisymmetric inlet channel in a fully opened state of a turbine channel, and after an air flow is compressed by an outer pressure section, an inner pressure section, a throat section and a throat expansion section, the air flow is divided by an extended outer casing 4 of a turbine engine and enters a turbine channel 6 and a ram channel 5 respectively.
The air inlet channel is used for a series-type combined power engine comprising a stamping channel and a turbine channel outer ring, and the axisymmetrical air inlet channel comprises: a central body 1, an inlet lip shroud 2 surrounding the central body, an inlet shroud 3, and an extendable turbine engine case 4;
the central body 1 is arranged on the turbine engine central fairing by means of a central body support 7;
the inlet lip cover 2 is arranged at the outer edge of the inlet outer cover, wherein a throat is formed between the middle part of the central body 1 and the inlet lip cover 2;
the extensible turbine engine outer casing 4 is arranged inside the air inlet channel and divides the inside of the air inlet channel into a stamping channel 5 and a turbine channel 6;
the size of the inlet of the turbine passage 6 is adjusted by controlling the extension and contraction of the extensible turbine engine outer casing 4, so that the turbine passage 6 is controlled to be opened or closed, the switching of the gas passage and the redistribution of the flow are completed, and the mode conversion is realized.
Specifically, in the present embodiment, the extendable turbine engine case may take a variety of configurations, such as: the extension and retraction of the turbine engine outer case are realized by providing a retractable mechanism at the front end of the turbine engine outer case and adjusting the length of the retractable mechanism. For example, it is also possible to adopt: the outer casing thin sleeve is used for driving the outer casing sleeve to move forwards and backwards to realize extension of the outer casing structure. The front and back movement of the telescopic mechanism or the sleeve can be realized by adopting hydraulic drive, a motor and other related drive parts capable of outputting drive force according to space and stress requirements, the drive parts are connected with a drive connecting rod, and the drive rod is connected with an extended outer box or sleeve through a screw.
Specifically, the flow rate of the gas flowing into the turbine passage 6 is determined by the size of the turbine passage inlet formed between the center body 1 and the extendable turbine engine case 4, which is determined according to the requirement. Assuming that the inlet axial length, determined by the flow rate required by the operating conditions of the turbine engine, is L, the adjustable range is also at least L.
In the turbo mode, this portion of the flow entering the turbine engine reacts with the fuel to provide thrust, and the flow diverted to the ram channel 5 is either directly exhausted through the ram channel 5 or used for air demand by the engine accessory system.
Specifically, in the present embodiment, the description of the embodiment is made only by taking the example of the conversion from the turbine engine operating state to the ramjet engine, and the process adjustment process for the conversion from the ramjet engine to the turbine engine is reversed. When the flight Mach number reaches the mode conversion Mach number, the turbine engine needs to gradually quit working, and the ramjet needs to be ignited and gradually takes over the work of the turbine engine. In this process, the turbine engine airflow demand is gradually reduced and the ramjet engine flow demand is gradually increased.
In order to reduce the flow of the turbine channel and increase the flow of the ram channel, the outer casing of the turbine engine is adjusted to extend forwards from the initial turbine mode position, the inlet of the turbine channel is gradually reduced, the air flow entering the turbine channel is reduced, correspondingly, the total capture flow of the air inlet channel is not changed, the flow entering the ram channel is increased until the flow of the ram channel reaches the maximum value after the mode conversion is finished, the flow of the turbine channel is reduced to the minimum, under the normal condition, in order to protect the turbine engine from being damaged at a high Mach number, the turbine channel is completely closed after the mode conversion is finished, no air flows flow flows into the turbine channel, and the capture flow of the air inlet channel completely flows into the ram channel.
In the process, the outer casing will have a passage area A duct Divided into two parts at all times, wherein the turbine engine passage area A turbojet Area A of ramjet ramjet . Still taking the example of the conversion from the operating state of the turbine engine to the ramjet engine, under the condition that the air inlet channel normally operates, the flow is relatively stable, the flow split is in direct proportion to the area of the inlet, namely the flow coefficients of the two channels at a certain moment are approximately the ratio of the area to the total area:
the trapped flow of the air inlet is a certain value, i.e., phi in And is not changed. And phi in ＝φ turbojet +φ ramjet Therefore, the flow dividing rate (coefficient) of the two channels is determined by the flow dividing area of the front end of the casing.
In the process of advancing the outer casing:
A turbojet (l) wherein 0<l<L
A ramjet F (l), wherein 0<l<L
Both monotonically decreasing, but the ratio of the two
Because the profile gradient of the inner wall surface of the central body is larger, the inlet of the turbine channel formed by the front end of the splitter plate and the profile is reduced more quickly, the ratio of the turbine shunting area to the stamping shunting area is monotonically decreased, namely the turbine channel ratio is gradually decreased, and the stamping channel ratio is gradually increased.
The ratio of the stamping channel is gradually increased until the area of the stamping channel is equal to the area A of the throat when the stamping channel is in butt joint with the throat th (ii) a The turbine channel is shifted to the inner wall surface of the throat, the flow area is reduced to 0, the flow dividing area of the turbine channel is gradually reduced in the process, the flow dividing area of the stamping channel is gradually increased, and therefore phi is turbojet Decrease of phi ramjet And the conversion from the captured flow of the air inlet to the ramjet is realized, and the conversion process of the mode of the air inlet is completed. The conversion process from ramjet to turbine is reversed.
Fig. 3 shows the flow coefficient of the inlet channel and the flow coefficient of the turbine and ram channels during the mode conversion process of the present embodiment, where the abscissa "d" represents the opening size and the ratio of the movement distance to the maximum movement distance of the turbine channel being completely closed, and the ordinate represents the flow coefficient and is defined as the ratio of the channel flow to the inlet channel capture flow. It can be seen that the scheme realizes the change of the two channels to the flow demand in the mode conversion process, the flow of the turbine channel is reduced, the flow of the stamping channel is increased, the total flow of the air inlet channel is not changed, and the stable transition of the flow and the thrust in the process can be realized.
The invention is not described in detail, but is well known to those skilled in the art.
The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations can be devised by those skilled in the art in light of the above teachings. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (4)
1. A combined power mode conversion method for an extended outer casing, the conversion method being directed to an axisymmetric inlet duct for a tandem combined power engine including a ram channel and a turbine channel outer ring, the axisymmetric inlet duct comprising: a centerbody, an inlet lip shroud surrounding the centerbody, an inlet shroud, an extendable turbine engine case;
the center body is supported by the center body on a turbine engine center fairing;
the air inlet lip cover is arranged on the outer edge of the air inlet cover, wherein a throat is formed between the middle part of the central body and the air inlet lip cover;
the turbine engine outer casing is arranged inside the air inlet channel, and the inside of the air inlet channel is divided into a stamping channel and a turbine channel;
the size of the inlet of the turbine channel is adjusted by controlling the extension and the contraction of the turbine engine outer casing, so that the turbine channel is controlled to be opened or closed, the switching of the gas path and the redistribution of the flow are completed, and the mode conversion is realized.
2. The method of claim 1, wherein the extending and retracting of the turbine engine case is performed by providing a retractable mechanism at a front end of the turbine engine case and adjusting a length of the retractable mechanism.
3. The method as claimed in claim 2, wherein the minimum distance of forward extension of the retractable mechanism is determined by the required turbine engine flow in the turbine mode, and the maximum distance is determined by the extension distance required to fully close the turbine passage.
4. The method of claim 1, wherein the centerbody has a diameter at a middle portion thereof that is greater than or equal to a diameter of a turbine engine case.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210411274.4A CN114837811A (en) | 2022-04-19 | 2022-04-19 | Combined power mode conversion method for extended outer casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210411274.4A CN114837811A (en) | 2022-04-19 | 2022-04-19 | Combined power mode conversion method for extended outer casing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114837811A true CN114837811A (en) | 2022-08-02 |
Family
ID=82565404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210411274.4A Pending CN114837811A (en) | 2022-04-19 | 2022-04-19 | Combined power mode conversion method for extended outer casing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114837811A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115788683A (en) * | 2022-11-30 | 2023-03-14 | 中国航发控制系统研究所 | Modal conversion control method based on combined engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3520138A (en) * | 1969-02-27 | 1970-07-14 | United Aircraft Corp | Convertible enginf |
| US4909031A (en) * | 1987-05-27 | 1990-03-20 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Combined multi-speed jet engine for the drive of airplanes and space vehicles |
| US5150571A (en) * | 1989-12-21 | 1992-09-29 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Device for exposing or shutting off a turbo-engine on the intake air side of the engine |
| CN109436347A (en) * | 2018-10-12 | 2019-03-08 | 北京动力机械研究所 | Engine binary channels list movable member air inlet regulating device |
| CN109915263A (en) * | 2019-04-10 | 2019-06-21 | 南京航空航天大学 | Axial symmetry bimodal air intake duct and Mode-switch method for combined engine |
| CN111692013A (en) * | 2020-07-03 | 2020-09-22 | 南京航空航天大学 | Axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine and control method |
-
2022
- 2022-04-19 CN CN202210411274.4A patent/CN114837811A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3520138A (en) * | 1969-02-27 | 1970-07-14 | United Aircraft Corp | Convertible enginf |
| US4909031A (en) * | 1987-05-27 | 1990-03-20 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Combined multi-speed jet engine for the drive of airplanes and space vehicles |
| US5150571A (en) * | 1989-12-21 | 1992-09-29 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Device for exposing or shutting off a turbo-engine on the intake air side of the engine |
| CN109436347A (en) * | 2018-10-12 | 2019-03-08 | 北京动力机械研究所 | Engine binary channels list movable member air inlet regulating device |
| CN109915263A (en) * | 2019-04-10 | 2019-06-21 | 南京航空航天大学 | Axial symmetry bimodal air intake duct and Mode-switch method for combined engine |
| CN111692013A (en) * | 2020-07-03 | 2020-09-22 | 南京航空航天大学 | Axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine and control method |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115788683A (en) * | 2022-11-30 | 2023-03-14 | 中国航发控制系统研究所 | Modal conversion control method based on combined engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2966039C (en) | Gas turbine engine with thrust reverser assembly and method of operating | |
| RU2413859C2 (en) | Combined cycle system interacting combustion chamber and nozzle | |
| USRE43731E1 (en) | Integrated air inlet system for multi-propulsion aircraft engines | |
| US20180045139A1 (en) | Gas turbine engine with axial movable fan variable area nozzle | |
| CN106285946B (en) | The channel of double-axle rotation deformation becomes geometry air intake duct without rider formula in wedge angle | |
| EP1984616B1 (en) | A gas turbine engine | |
| US4909031A (en) | Combined multi-speed jet engine for the drive of airplanes and space vehicles | |
| US20090053058A1 (en) | Gas turbine engine with axial movable fan variable area nozzle | |
| US6668542B2 (en) | Pulse detonation bypass engine propulsion pod | |
| US20090003997A1 (en) | Variable shape inlet section for a nacelle assembly of a gas turbine engine | |
| CN105736178B (en) | Combined cycle engine | |
| US20040006969A1 (en) | Variable area nozzle | |
| CN112228246B (en) | Rocket-based detonation and stamping combined cycle engine and use method and application thereof | |
| US5852928A (en) | Thrust reverser with extendible pivoting baffle | |
| EP3004612A2 (en) | Dual-mode plug nozzle | |
| CN114837811A (en) | Combined power mode conversion method for extended outer casing | |
| JPS6053176B2 (en) | Propulsion nozzle | |
| US4000611A (en) | Variable area, load balancing nozzle | |
| CN110645100A (en) | Ma0-6+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet | |
| CN114753930A (en) | Combined power mode conversion method based on axisymmetric air inlet channel configuration characteristics | |
| CN111692013A (en) | Axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine and control method | |
| CN112360645A (en) | Tandem turbine/double-mode stamping combined engine mode conversion device | |
| CN117028059A (en) | Separate exhaust throat offset type pneumatic vector spray pipe based on variable cycle engine | |
| CN113153577B (en) | Multistage rotary detonation rocket stamping combined engine | |
| CN111594348B (en) | Starting control method for rocket-based combined cycle engine air inlet |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |